Nozzle and method for washing gas turbine compressors

ABSTRACT

A nozzle ( 54 ) for cleaning a gas turbine unit ( 1 ) during operation. The invention further relates to a method for washing a gas turbine unit ( 1 ) during operation. The nozzle ( 54 ) is arranged to atomize a wash liquid in the air stream in an air intake ( 2 ) of the gas turbine unit ( 1 ) and comprises a nozzle body ( 40 ) comprising an intake end ( 41 ) for intake of said wash liquid and outlet end ( 55 ) for exit of said wash liquid. The nozzle further comprises a number of orifices ( 42, 46; 42, 46, 60 ) that are connected to the outlet end ( 55 ) and respective orifice ( 42, 46; 42, 46, 60 ) is arranged at a suitable distance from a center axis ( 49 ) of said nozzle body ( 40 ), whereby the local density of the injected wash liquid in a desired area can be increased with preserved droplet size and thereby the efficiency of the cleaning process can be significantly improved at the same time as the risk for damaging the components in the gas turbine unit is significantly reduced.

TECHNICAL FIELD

This invention relates to washing of gas turbines and particularly to anozzle for washing a gas turbine unit during operation. Further theinvention relates to a method for washing of said gas turbine unit underoperation.

DESCRIPTION OF PRIOR ART

The invention relates to the general art of washing gas turbine equippedwith axial compressors or radial compressors. Gas turbines comprise of acompressor for compressing air, a combustor for combusting fuel togetherwith the compressed air and a turbine driving the compressor. Thecompressor comprises in turn multiple compression stages, where acompression stage comprises of a rotor disc and subsequent stator discwith vanes.

Gas turbines in operation consumes large quantities of air. The aircontains contaminants in form of small particles, called aerosols, thatenters the compressor with the air stream. A majority of these particleswill follow the air stream and exit the gas turbine with the exhaust.However, there are particles with the properties of sticking on tocomponents in the engine's gas path. These particles build up a coatingon the components, reducing the aerodynamic properties. The coatingresult, in an increase in the surface roughness which result in adecrease in the pressure gain as well as a reduction of the air flowthat the compressor compresses. For the gas turbine unit it results in adecrease in efficiency, a reduced mass flow and a reduced pressureratio. To reduce the contamination modern gas turbines are equipped withfilters for filtering of the air to the compressor. These filters canonly capture a portion of the particles. To maintain an economicoperation of the gas turbine, it is found necessary to regularly cleanthe compressor gas path components to maintain the good aerodynamicproperties.

Different methods for cleaning gas turbine compressors are previouslyknown. To inject crushed nut shells into the air stream is shown to bepractical. The disadvantage with the method is that nut shell materialmay find its way into the internal air system of the gas turbine withthe consequence of clogging of channels and valves. Another method forcleaning is based on wetting of the compressor components withdetergent. The detergent is injected with nozzles spraying it into theair stream of the compressor.

Stationary gas turbines vary much in size. The largest gas turbines onthe market have a rotor diameter in excess of two meters. This meansthat the air duct upstream of the compressor will thereby also havelarge geometries. For a gas turbine with a two meter diameter rotor mayhave more than two meter distance to the opposite duct wall. With theselarge geometries there may be difficulties in injecting washing fluidinto the part of the duct with the core air stream. If the liquidfollows the core air stream the surface of the rotor blades and statorvanes will essentially be wetted whereby a good wash will be obtained.If the liquid on the contrary will follow close to the duct wall, theliquid will in an unsatisfactory way wet the blades and vanes. Further,a portion of the liquid will be caught by the boundary layer air streamby the duct wall and will there form a liquid film which is transportedinto the compressor by the air stream. This liquid will not participatein washing of the compressor and can cause damage of, for example, theliquid fills the gap between the rotor tip and compressor casing.

In contrary to large gas turbines with large geometries there are smallgas turbines with moderate dimensions on the inlet air duct. For smallergas turbines the spray can more easily penetrate in to the core airstream. Experience from actual wash installations on gas turbines showthat the spray from conventional nozzles penetrated the air stream sometens of a centimeter. For most small and medium size gas turbines thisis sufficient for satisfactory wetting of the rotor blades and statorvanes. One problem is that conventional nozzles can not penetrate theair stream of large gas turbines.

A preferred cleaning method is based on wetting the compressorcomponents with a washing fluid. The fluid is injected through a nozzlethat atomizes the liquid into a spray in the air stream entering thecompressor. The washing fluid may consist of water or a mixture of waterand chemicals. During injection of the wash liquid the gas turbine rotoris cranked with its starter motor. This method is called “crank wash” or“off-line” wash and is characterized by that the gas turbine does notfire fuel during washing. The spray is created by the washing liquidbeing pumped through the nozzles which then atomizes the fluid. Thenozzles are installed on the duct walls upstream of the compressor'sinlet or on a frame temporarily installed in the duct.

The method is characterized by the compressor components soaked withcleaning fluid where contamination is released by act of the chemicalstogether with mechanical forces from the rotation of the shaft. Themethod is considered efficient and fruitful. The rotor speed at crankwash is a fraction of the speed prevailing at normal operation. Oneimportant property with crank washing is that the rotor is rotating atlow velocity whereby there is little risk for mechanical damage. Whilepractising this method the gas turbine must be taken out of servicewhich may cause production loss and costs.

U.S. Pat. No. 5,011,540 discloses a method for wetting of compressorcomponents while the gas turbine is in operation. This method is knownas “on-line” washing and is characterized by fuel is being fired in thegas turbine combustor during washing. The method has in common with thecrank wash method in that liquid is injected up stream of thecompressor. This method is not as efficient as the crank wash method.The lower efficiency relates to poor washing mechanisms prevailing athigh rotor speeds when the gas turbine is in operation. For example, acorrect dose of liquid must be injected as a too high dose may causemechanical damage to the compressor and a too low dose may cause poorwetting of the compressor components. Further, the droplets must besmall else large droplets may cause erosion damage from the collision ofthe droplets with the rotor and stator blades.

A gas turbine compressor is designed to compress the incoming air. Inthe rotor the rotor energy is transformed into kinetic energy by therotor blade. In the subsequent stator vane the kinetic energy istransformed into a pressure rise by a velocity reduction. To enable thecompression process high velocities are required. For example, it iscommon that the rotor tip of modern gas turbines exceeds the velocity ofsound. This means that the axial velocity in he compressor inlet is veryhigh, typically 0.3-0.6 Mach or 100-200 m/s.

According to state of the art technology, wash liquid is pumped at highpressure in a conduit to a nozzle on the duct wall upstream of thecompressor inlet. In the nozzle the liquid reaches high velocity whereofatomization takes place and a spray of droplets are formed. The spray iscaught by the air stream and the droplets carried with the air streaminto the compressor. By the choice of nozzle design small or largedroplets can be formed. Alternatively, a nozzle for small droplets canbe used. With small droplets in this context means droplets with adiameter of less than 150 μm. The disadvantage with small droplets isthat have a small mass and thereby low inertia when leaving the nozzle.The droplets velocity is quickly reduced by the air resistance and therange is therefore limited. Alternatively can a nozzle for largedroplets be selected. With large droplets in this context means dropletswith a size greater than 150 μm. Large droplets have the advantage of ahigh inertia when leaving the nozzle. The relationship between thedroplet size and its mass is that the mass is proportional to the radiuscubed. For example, a 200 μm droplet is twice the size of a 100 μmdroplet but has eight times its mass. Through the greater mass follows agreater range compared to the smaller droplet. The disadvantage with thelarger droplet is that when the droplets are caught by the air streamthey also achieve high velocity towards the compressor. At impact withthe blade surface large energies are transferred whereof there may bedamage on the blade surface. The damages will appear as erosion damages.

To achieve a good washing effect the spray must penetrate into the coreof the air stream. A difficulty with the on-line wash method, e.g. asshown in U.S. Pat. No. 5,011,540 is to get the liquid into the core ofthe air duct. As previously mentioned there are very high velocities inthe air duct which drags the wash liquid before it has penetrated intothe core of the air stream. Thereby, the droplets must be small as toavoid erosion damage. However, small droplets show a disadvantage inthis respect. Small droplets has low inertia, as off its low mass, andquickly loose velocity when the atomization is completed. In contrary tolarge droplets which has a good ability to maintain initial velocityover a longer range. A spray of small droplets has therefore an impairedability to penetrate into the core of the air stream. This problem isespecially evident for large gas turbines with large air duct geometrieswhere the distance from the nozzle to the centre of the air duct islong.

In summary, the washing of gas turbines, especially during gas turbineoperation, is associated with a number of problems.

SUMMARY OF THE INVENTION

One objective with the invention is to provide a nozzle and a method forwashing of a gas turbine during operation in an efficient and safe way.

This and other objectives are achieved by this invention with a nozzleand a method which have the characteristics defined by the independentclaims. The preferred embodiments are defined in the dependent claims.

For the purpose of clarification the use of “angle against shaft centre”or “angle against centre axis” means the angle between the direction ofa liquid stream from a nozzle and a reference surface parallel with thecentre axis through the nozzle body.

According to the first aspect of the invention, a nozzle is disclosedfor washing of a gas turbine unit. The nozzle is arranged for atomizinga washing fluid in the air stream of an air inlet duct to said gasturbine unit including a nozzle barrel which, in turn, includes an inletend for inlet of said washing fluid and an outlet end for outlet of saidwashing fluid. The nozzle includes further multiple orifices at theoutlet end where the orifice is arranged at a defined distance from thenozzle barrel shaft axis.

According to a second aspect of the invention, a method is disclosed forwashing of a gas turbine unit comprising of atomizing a wash fluid in anair intake of said gas turbine unit comprising of an inlet end forentering wash liquid and an exit end for releasing said wash fluid. Themethod is characterized by the formation of said atomized wash fluid byfeeding said wash fluid to said orifice at nozzle exit end, whereof eachorifice is arranged at suitable distance from the nozzle body centreaxis.

The invention is based on the idea of increasing the local density ofthe atomized wash fluid in a specified volume by feeding the wash fluidthrough multiple orifices of the nozzle barrel arranged at suitabledistances from the nozzle barrel centre axis. This arrangement willallow an improved penetration of the spray into the air stream withmaintained droplet size, or even with decreased droplet size, i.e. thenozzle according to the invention will allow wash fluid to be injectedinto the core of the air stream in the air duct without increasing thedroplet size. Thereby will the risk for erosion damage on gas turbinecomponents be reduced while a high efficiency wash will be obtainedcompared to conventional solutions.

Another advantage is that the nozzle may be equally applied to gasturbines with small geometries as well as gas turbines with largegeometries.

Yet another advantage is that washing of components in the gas turbineunit can be practised during gas turbine operation with significant costsavings. Another advantage is that the nozzle according to the inventioncan be used for crank washing.

According to preferred embodiment of the invention each orifice ispointing at an angle towards the nozzle centre axis so that the liquidwill exit the orifice towards the centre axis. Thereby will the liquidjet from an orifice be within an angle range of 0-80° and preferredwithin an angle range 10-70°.

By directing the orifice in a suitable angle towards the nozzle centreaxis a preferred coverage can be obtained which means that the sprayshall have a spray angle as to satisfactory wet the rotor blades andstator vanes within the segment of the compressor inlet where the spraywill act. The condition for coverage is thereby fulfilled by selecting anozzle with the appropriate spray angle. By directing the orifice in asuitable angle towards the centre axis an increased spray density canlocally be obtained and a better penetration of the fluid into the airstream can be obtained.

The advantage by the invention is further enhanced by the spray shapeshows a smaller projected area against the air stream compared to thespray from a conventional nozzle. By the smaller projected area thespray will not that easy be caught by the air stream but insteadpenetrate better into the air stream.

According to the preferred embodiment of the invention each of the saidorifices is positioned at essentially the same distance from said centreaxis and at essentially the same angle towards the centre axis. Thisdesign is found to be advantageous in increasing the local density ofthe spray in the desired area and thereby reduce the risk for erosiondamage on the gas turbine components while maintaining a high washingefficiency.

According to an exemplified embodiment of the invention are the orificearranged as to point towards the centre axis and have a commonconjunction point in the range 5-30 cm from said orifice.

Preferably shall the liquid pressure be in the range 35-175 bar.

Preferably are the orifices arranged as to bring the liquid through theorifice at a velocity in the range 70-250 m/s.

According to the preferred embodiment of the invention are the orificesof essentially the same design.

According to a preferred embodiment of the invention is the orificedesigned to form a spray with an essentially circular spray pattern,i.e. a spray with a essentially circular cross section. Alternativelymay the orifice be arranged to form a spray of an essentially ellipticalshape or an essentially rectangular shape.

According to a preferred embodiment of the invention there are twoorifices in connection to said outlet end of the nozzle barrel. By usingtwo orifices somewhat apart from each other and allowing the sprays toconverge at a point after completion of the atomization, the core of theair stream is reached. Within the volume where the two sprays merge, thedensity of the spray will double and increasing the impact force on thesurrounding air, followed by a better penetration into the air stream,followed by a more efficient wash and a reduced risk for erosion damagedon the compressor components as the droplets are allowed to remainsmall, i.e. with a diameter less than 150 μm.

Additional advantages with the invention will be obvious by thefollowing detailed descriptions in the preferred embodiments of theinvention.

BRIEF DESCRIPTION OF THE DRAWINGS

The preferred embodiments of the invention will now be described indetail with reference to the attached drawings where:

FIG. 1 shows a part of a gas turbine and positioning of nozzles forinjecting wash fluid into the air stream.

FIG. 2 shows atomization of wash fluid in a nozzle.

FIG. 3 shows a conventional nozzle for injection of wash liquid into agas turbine inlet

FIG. 4. shows the nozzle according to the invention and a firstexemplary embodiment of the invention.

FIG. 5 shows the nozzle according to the first exemplary embodiment ofthe invention.

FIG. 6 shows the nozzle according to the invention and a secondexemplary embodiment of the invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

With reference to FIG. 1, a section of a gas turbine 1 and thepositioning of nozzles for injecting of wash liquid into a compressorinlet are shown. The gas turbine comprises of an air intake 2 which isrotationally symmetric to axis 3. The air flow is indicated by arrows.Air enters radially to be rerouted and flow parallel to the machineshaft through compressor 14. Compressor 14 has an inlet 4 at the leadingedge of the first disc of stator vanes. After disc 5 with stator vanesfollows a disc 6 with rotor blades, followed by a disk 7 with statorvanes, and so on. The air intake has an inner duct wall 8 and an outerduct wall 9. A nozzle 10 is installed on the inner duct wall. A conduit11 connects the nozzle with a pump (not shown) which supplies the nozzlewith wash fluid. After passing nozzle 10 the liquid atomizes and forms aspray 12. The droplets are carried with the air stream to compressorinlet 4. Alternatively, nozzle 13 is installed on the outer air ductwall 9.

FIG. 2 shows atomization of a fluid from a nozzle. A nozzle 20 with anaxis 24 has an inlet 21 for the wash fluid and an orifice 22 where theliquid exit the nozzle. The orifice area and liquid pressure is adaptedfor a specific flow rate. Orifice 23 has a hole where the wash fluidflows. A nozzle for gas turbine compressor washing has an orifice areaand a liquid pressure such as that the liquid velocity through theorifice is high, in the order of 100 m/s.

The direction of flow will be direction of which the orifice ispointing. If the orifice is circular a spray with a circular crosssection will form. The spray will propagate with one component in thehole's axial direction and another component in the directionperpendicular to the axial direction. According to FIG. 2, the geometryof the spray can be described as a cone with base C and height B andwhere C is the cone's diameter.

After the liquid has left the orifice the atomization takes placeimplying that the liquid first is fragmentized followed by a breakdowninto small particles. The particles finally take the shape of a spheregoverned by that the surface tension is minimized. At a distance A fromthe orifice 22 according to FIG. 2, the atomization is essentiallycompleted. A spray consisting of droplets of varying size is thenformed. For a nozzle in this gas turbine application, operating at aliquid pressure of 70-140 bar, the distance A is typically 5-20 cm. Atan additional distance B the droplets have continued to propagate but itis now greater distances between the droplets. When the distancesbetween the droplets become bigger, this means that the spray density isreduced. If the was fluid is assumed to be water, the density beforeatomization takes place is 1000 kg/m³. At distance B the spray ischaracterized as having a less density than at distance A where densityis defined as the number of particles by volume air locally. For anozzle in this gas turbine application operating at a liquid pressure of50-140 bars, the density at A is typically 20 kg/m³.

It is evident that when the droplets collide with the air molecules thevelocity is reduced. In the context of this invention, a key issue ishow far the spray penetrates the air before the air stream has reachedthe compressor inlet. A single droplet with a certain initial velocitywill quickly loose its initial velocity and asymptotically reach zerovelocity. The man skilled in the art can estimate the droplets velocityas a function of the distance from the orifice by the use of the balancefor the aerodynamic drag force and the force by inertia. For the sprayas a whole, it shall displace the air in its way. This can be seen as ithas an impinging force on the air characterized by its density, volumeflow and velocity. The impact force can be estimated as:F=dens*Q*V*Cd  (equation. 1)where

-   F=impact force-   dens=density-   Q=volume flow-   V=velocity-   Cd=de-acceleration coefficient

The de-acceleration coefficient is estimated from the balance betweenthe droplet aerodynamic drag force and the force of inertia.

For the wash procedure according to the invention it is important thatthe spray well penetrates the air stream. This will occur with a highimpinging force as per the definition above. Further, for a good washresult it is required that the spray has a good coverage. By coveragemeans that the spray shall have a spray angle to satisfactory coverrotor blades and stator vanes within the segment that the spray isacting. The condition for coverage is satisfied by a nozzle with adefined spray angle.

The spray as per above is characterized by its impingement force beinghighest at the nozzle orifice and the decrease with the distance fromthe orifice. If the wash fluid is assumed to be water, the density is1000 kg/m³. The area is estimated from the hole diameter. At eachdistance from the nozzle orifice the impingement force can then beestimated from equation 1. The increased area with the increaseddistance result in that the impingement force will asymptotically bezero.

FIG. 3 show the same spray as shown in FIG. 2, where identical partshave the same reference numerals as in FIG. 2. FIG. 3 shows aconventional nozzle. Distance D is the distance the spray has penetratedthe air stream before the air stream has transported the droplets to thecompressor inlet. The condition for coverage is fulfilled by choice ofnozzle with spray angle 34 resulting in coverage E at distance D.

In the description above a spray with a circular projection is assumed.By selecting a nozzle with appropriate orifice geometry, an elliptic orrectangular spray is formed. In the art of gas turbine compressorwashing non-circular sprays are used.

With reference to FIG. 4 and FIG. 5, a first preferred embodiment of theinvention is shown. The invention relates to a nozzle performing a spraywith an increased impaction force. With the increased impaction forcewill the distance D according to FIG. 3, increase and thereby will theearlier identified problem of penetration into the core of the airstream, be eliminated or partly eliminated. FIG. 4 shows a nozzleaccording to the invention. A nozzle 54 includes a nozzle barrel 40 witha centre axis 49 with an opening 41 for entering a washing fluid and afirst orifice 42 at the outlet end 55 and orifice 42 has an opening 43where washing fluid exits the nozzle. The first orifice 42 is positionedoff side the centre axis 49 and with an angle pointing towards thecentre axis so that the formed spray is directed to the centre axis. Thespray that is formed is circular. The spray geometry can be described asa cone with a base line with one end 44 and another end 45 and tip 43.Nozzle 54 has a second orifice 46 at the outlet end 55 and orifice 46has an opening 47 where fluid exits the nozzle. Orifice 46 is positionedoff side the centre axis 49 and with an angle pointing towards thecentre axis so that the formed spray is directed to the centre axis. Thespray that is formed is circular. The spray geometry can be described asa cone with a base line in between one end 45 and another end 48 and tip47. According to the preferred embodiment of the invention the orificesare directed at angles towards the centre axis so that the fluid fromone orifice is preferably within the angle range 0-80° and additionallypreferably within the angle range 10-70°.

The two orifice openings have the same hole area and the alike geometrywhereby the incoming liquid is equally distributed between the twoorifice 42 and 46. The two orifice openings are directed-towards thecentre axis at a junction point 57 at distance J from the orificeopenings. Distance J is within the range 5-20 cm.

The liquid is atomized when exiting the orifice openings 43 and 47. At adistance F from the orifice openings the atomization is in generalcompleted. The two sprays will now merge whereby a zone 53 is formedwith increased density by merging of the two sprays. Zone 53 is limitedby points 50, 52, 45, 51 and 50. With the increased density follows anincreased impingement force according to equation 1. It is the purposeof the invention to increase the impingement force. By a suitable nozzlespray angle and spray direction the requirements of coverage H atdistance G is fulfilled.

FIG. 5 shows the nozzle in the perspective X-X, where like parts areindicated with the same reference numerals as in FIG. 4. FIG. 5 showsthe orientation of the orifices 42 and 46 with respect to the directionof the air stream. The direction of the air stream is indicated witharrows.

The effect of the invention is further improved by the fact that thespray in accordance with FIG. 4 discloses a projected area against theair stream that is smaller in comparison with the spray from aconventional nozzle. With the direction of stream in accordance withFIG. 5 the projected area against the air stream the area between thepoints 47, 50, 43, 52, 48, 45, 44, 51 and 47 in FIG. 4. This area shouldbe compared with the projected area that results at use of aconventional nozzle in accordance with FIG. 3, where this areaconstitutes the area between the points 22, 31, 32 and 22. The area inFIG. 3 is larger than corresponding area in FIG. 4. Due to the smallerprojected area, the spray is not caught by the air stream that easy andthereby the spray is able to penetrate the air stream in a moreeffective manner.

With reference now to FIG. 6, a nozzle in accordance with the presentinvention that exemplifies a second embodiment of the invention will beshown. FIG. 6 shows the nozzle in the perspective X-X, where like partsare indicated with the same reference numerals as in FIG. 4. As thefunction of this embodiment of the nozzle in accordance with the presentinvention is substantially the same as the function of theabove-described embodiment such a description of the function is omittedhere. FIG. 6 shows the orientation of the orifices 42, 46 and 60 withrespect to the direction of the air stream. The orifice 60 has, as theorifices 42 and 46, an opening 61 where the fluid leaves the nozzle. Thedirection of the air stream is indicated with arrows. The third orifice60 is mounted at the side of the axis centre at the same distance fromthe axis centre 49 and at the same angle as the orifices 42 and 46 suchthat the formed spray is directed against the axis centre in acorresponding manner as in the above-discussed embodiment.

Even if the presently preferred embodiments of the invention has beendescribed, it is from the above description obvious for the man skilledwithin the art that variations of the present embodiments can berealized without departing from the scope of the principles of theinvention.

Thus, the intention is not that the invention should be limited only tothe structural and functional elements described with reference to theembodiments but only by the appended patent claims.

1. A nozzle for washing a gas turbine unit arranged to atomize a washliquid in the air stream in an air intake of said gas turbine unitcomprising a nozzle body, said nozzle body comprising: an intake end forintake of said wash liquid and outlet end for exit of said wash liquid,and a center axis; a number of orifices connected to the outlet end andhaving means for atomizing wash liquid, wherein the atomizing meanscomprises one or more orifice openings; wherein said orifices aredirected at an angle towards said center axis at a junction point at adistance within a range of 5-30 cm from said orifice openings, andwherein said orifices are configured so that liquid emanates from saidorifice openings at a spray angle that is within an angle rangeof >0-80°; and means for installing said nozzle on the air intake ofsaid gas turbine unit.
 2. The nozzle according to claim 1 wherein eachof said orifices is arranged at substantially the same distance fromsaid center axis and at substantially the same angle with respect tosaid center axis.
 3. The nozzle according to claim 1 wherein a pressureof said wash liquid at said orifices is within the range of 35-175 bar.4. The nozzle according to claim 3 wherein said orifice openings arearranged to, in cooperation with said pressure, cause said liquid tostream out with a liquid velocity in the range of 50-250 m/s.
 5. Thenozzle according to claim 1 wherein said orifice openings havesubstantially the same design.
 6. The nozzle according to claim 1wherein said orifices are arranged to form a spray into a form inaccordance with any one of from the group of substantially circular,substantially elliptical, or substantially rectangular.
 7. The nozzleaccording to claim 1 wherein two orifices are connected to said outletend.
 8. A washing device for washing a gas turbine unit comprising atleast one nozzle arranged to atomize a wash liquid in the air stream inan air intake of said gas turbine unit comprising a nozzle body, saidnozzle body comprising: an intake end for intake of said wash liquid andoutlet end for exit of said wash liquid, and a center axis; a number oforifices connected to the outlet end and having one or more orificeopenings configured for atomizing wash liquid, wherein said respectiveorifices are directed at an angle towards said center axis at a junctionpoint at a distance within a range of 5-30 cm from said orificeopenings, and wherein said orifices are configured so that liquidemanates from said respective orifice openings at a spray angle that iswithin an angle range of >0-80°; and means for installing said at leastone nozzle on the air intake of said gas turbine unit.
 9. The washingdevice according to claim 8 wherein each of said orifices is arranged atsubstantially the same distance from said center axis and is angled atsubstantially the same angle with respect to said center axis.
 10. Thewashing device of claim 8 wherein a pressure of said wash liquid at saidorifices is within the range of 35-175 bar.
 11. The washing device ofclaim 10 wherein said orifice openings are arranged to, in cooperationwith said pressure, cause said liquid to stream out with a liquidvelocity in the range of 50-250 m/s.
 12. The washing device of claim 8wherein each of said orifice openings have substantially the samedesign.
 13. The washing device of claim 8 wherein said orifices arearranged to from a spray into a form in accordance with any one of fromthe group of substantially circular, substantially elliptical, orsubstantially rectangular.